Power device for aircraft and aircraft comprising such power device

Abstract

The invention relates to a power device for an aircraft and an aircraft comprising such a power device. The present invention relates to a power plant (151) for an aircraft and a corresponding aircraft, the power plant comprising: a propulsion system (150) comprising a core (152) enclosed in an enclosure (154) and having a combustion chamber (158); a supply tube that delivers dihydrogen to the combustion chamber (158) by passing through the housing (154) at the injection region (210); and a closed enclosure (250) delimited by first and second walls and housing the downstream tube, a treatment system (202, 204, 206) for treating dihydros, and an injection zone (210) wherein the first wall (251a) is formed by a portion of the housing (154). By this arrangement, the footprint and weight of each of the jackets are reduced as at least one wall of the jackets is formed by the outer shell of the propulsion system.

Description

Technical Field

[0001] The invention relates to a power plant for an aircraft engine operating with dihydrogen and to an aircraft comprising at least one such power plant. Background Art

[0002] For locomotion, an aircraft conventionally comprises at least one power plant comprising a propulsion system, such as a turbojet engine. Such a propulsion system comprises a core enclosed in a casing, which core comprises, from upstream to downstream, in particular a compressor, a combustion chamber and a turbine.

[0003] In order to reduce the carbon dioxide (CO2) emissions of aircraft engines, it is known to use dihydrogen as fuel. The aircraft then comprises a dihydrogen tank and the propulsion systems are supplied with dihydrogen by means of pipes extending inside the aircraft between the tank and each propulsion system and on which treatment systems such as pumps, heaters and valves are mounted.

[0004] In the event of an accident on the supply line between the tank and the engine, safety must be ensured. To this end, it is known to implement various safety systems.

[0005] While this arrangement is effective, it requires heavy equipment with a large footprint and there is a need to find a novel arrangement in which, inter alia, the footprint and weight are reduced. Summary of the invention

[0006] One object of the invention is to propose a power plant supplied with dihydrogen and comprising treatment systems enclosed in an enclosure one wall of which is formed by the outer casing of the propulsion system of the power plant.

[0007] For this purpose, a power plant for an aircraft is proposed, the power plant comprising:

[0008] - Nacelle,

[0009] a propulsion system housed in the nacelle and comprising a core enclosed in a casing and having a combustion chamber,

[0010] a supply pipe suitable for conveying dihydrogen to the combustion chamber by passing through the casing in the injection zone,

[0011] at least one treatment system arranged on the supply pipe and suitable for treating said dihydrogen transported in the supply pipe, and

[0012] A closed enclosure delimited by a first wall and a second wall and housing a downstream pipe of the supply pipe, at least one treatment system, and an injection zone, wherein the first wall is formed by a portion of the outer shell.

[0013] By this arrangement, the footprint and weight of each enclosure is reduced, since at least one wall of the enclosure is formed by the outer shell of the propulsion system.

[0014] According to a particular embodiment, the enclosure comprises at least one ventilation system suitable for exhausting the gases present in the enclosure to the outside of the aircraft.

[0015] Advantageously, at least one ventilation system takes the form of a first air inlet that passes through the second wall and through which air from outside the aircraft enters the enclosure, and a first air outlet that passes through the second wall and through which gas present in the enclosure is discharged to the outside of the aircraft.

[0016] Advantageously, at least one ventilation system takes the form of a pressure limiter mounted on the second wall and through which the gas present in the enclosure is exhausted to the outside of the aircraft.

[0017] According to a specific embodiment, the cladding is formed by a first sub-cladding, and a second sub-cladding, the injection zone is arranged in the first sub-cladding, and the second sub-cladding is separated from the first sub-cladding by a partition wall, wherein the downstream pipe passes through the second sub-cladding and then passes through the first sub-cladding by passing through the partition wall to reach the injection zone, wherein each sub-cladding is closed and bounded by a first wall, a second wall and a partition wall, wherein the first wall defining each sub-cladding is formed by a part of the outer shell.

[0018] According to a particular embodiment, the power unit comprises a ventilation system in the form of a second air inlet which passes through the second wall of the first sub-shell and through which air from outside the aircraft enters the first sub-shell, a second air outlet which passes through the second wall of the second sub-shell and through which the gas present in the second sub-shell is discharged to the outside of the aircraft, and an air duct which passes through the partition wall and emerges on one side in the first sub-shell and on the other side in the second sub-shell.

[0019] According to a particular embodiment, the power plant comprises a ventilation system in the form of a third air inlet, through which the second wall of the first sub-shell is penetrated and through which air from outside the aircraft enters the first sub-shell, and a third air outlet, through which the second wall of the first sub-shell is penetrated and through which the gas present in the first sub-shell is discharged to the outside of the aircraft.

[0020] Advantageously, the downstream pipe can pass through the partition wall in a sealing manner.

[0021] Advantageously, at least one sub-enclosure has a ventilation system in the form of a pressure limiter mounted on the second wall of said sub-enclosure and through which the gas present in said sub-enclosure is exhausted to the outside of the aircraft.

[0022] Advantageously, at least one treatment system comprises a treatment portion in which dihydrogen is treated and a non-treatment portion in which dihydrogen is not present, the treatment portion and the non-treatment portion being sealed from each other, the treatment system being arranged through an opening in the second wall and sealably fastened to the second wall, and the treatment portion being positioned in the enclosure or a corresponding sub-enclosure, and the non-treatment portion being positioned outside the enclosure or a corresponding sub-enclosure.

[0023] The invention also proposes an aircraft comprising a dihydrogen tank and at least one power plant according to one of the aforementioned variants, wherein the supply pipe is fluidically connected to the dihydrogen tank.

[0024] The invention also proposes an aircraft comprising a dihydrogen tank and at least one power plant according to one of the aforementioned variants, wherein the supply pipe is fluidically connected to the dihydrogen tank. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The foregoing and other features of the present invention will become more apparent upon reading the following description of an exemplary embodiment, which description is given with reference to the accompanying drawings, in which:

[0026] Figure 1 is a side view of an aircraft comprising a power plant according to the invention,

[0027] Figure 2 is a schematic side view of a power device according to a first embodiment of the present invention,

[0028] Figure 3 is a schematic side view of a power device according to a second embodiment of the present invention,

[0029] Figure 4 is a schematic perspective view of a power device according to a third embodiment of the present invention,

[0030] Figure 5 is a schematic detailed view of a variant of the invention, and

[0031] Figure 6 An example of a control unit implemented in the present invention is schematically shown. DETAILED DESCRIPTION

[0032] In the following description, position-related terms are given with reference to the aircraft in a forward-travel position, i.e. Figure 1 As shown, arrow F shows the forward direction of the aircraft.

[0033] In the following description, by convention, the longitudinal axis of the propulsion system, parallel to the longitudinal axis of the aircraft oriented positively forward in the forward travel direction of the aircraft, is referred to as X, the lateral axis which is horizontal when the aircraft is on the ground is referred to as Y, and the vertical axis or vertical height when the aircraft is on the ground is referred to as Z, the three axes X, Y and Z being orthogonal to each other.

[0034] Figure 1 An aircraft 100 is shown having a fuselage 102 on either side of which wings 104 are fastened. Under each wing 104 at least one power plant 151 is fastened, the power plant comprising a nacelle 149 consisting of a fairing 147 forming an aerodynamic outer surface.

[0035] Figure 2 A power plant 151 according to a first embodiment of the invention is shown, the power plant further comprising a propulsion system 150 , which is shown schematically and is accommodated inside the nacelle 149 .

[0036] exist Figure 2 In the embodiment of the invention shown, the propulsion system 150 is a turbojet engine comprising a core 152 enclosed in a casing 154 that is substantially cylindrical about a longitudinal axis X.

[0037] Outside air enters the nacelle 149 through an opening provided in the fairing 147 in front of the nacelle 149 .

[0038] Inside the nacelle 149 , the air flow is divided into a main flow 10 and a secondary flow 20 . The main flow 10 enters the core 152 to supply the combustion chamber 158 with dioxygen, and the secondary flow 20 flows around the core 152 and then is discharged at the rear of the nacelle 149 .

[0039] Thus, the casing 154 is open at the front to allow the main flow 10 to be introduced into the core 152, and is open at the rear to allow the gases produced by combustion to be discharged through the nozzle. Here, the core 152 includes, from upstream to downstream, a compressor 156, a combustion chamber 158 and a turbine 160. The compressor 156 and the turbine 160 are provided with blades that rotate around the longitudinal axis X.

[0040] Thus, the main flow 10 continuously passes through the compressor 156, where it is compressed, and then injected into the combustion chamber 158, where it is mixed with fuel. The gas produced by the combustion then passes through the turbine 160 and rotates the turbine. The turbine 160 in turn rotates the compressor 156, and then the gas is discharged at the rear.

[0041] The power plant 151 also includes supply pipes 170a-170b that allow dihydrogen to be delivered from a dihydrogen tank 172 of the aircraft 100 to the combustion chamber 158. The supply pipes 170a-170b are fluidically connected to the dihydrogen tank 172 and here, the supply pipes meander outside the housing 154 to the combustion chamber 158, the supply pipes reaching the combustion chamber by passing through the housing 154 in the injection zone 210.

[0042] The tubes 170a-170b are divided into an upstream tube 170a and a downstream tube 170b.

[0043] exist Figure 2 In the embodiment of the invention shown, the downstream pipe 170 b is provided in the injection zone 210 with an injector manifold 184 provided with injectors 185 which descend through the casing 154 into the combustion chamber 158 .

[0044] In order to prepare the dihydrogen upstream of the combustion chamber 158, the power plant 151 comprises at least one treatment system 202, 204, 206 (such as a heater, a pump, etc.) suitable for treating the dihydrogen circulating in the supply pipes 170a-170b.

[0045] Each treatment system 202, 204, 206 (here at least three in number) is arranged along the supply pipes 170a-170b, and more particularly on the supply pipes 170a-170b, so as to interact directly with the dihydrogen circulating in the supply pipes.

[0046] The power device 151 comprises an enclosure 250 delimited by walls 251a-251b, ie a first wall 251a and a second wall 251b. The first wall 251a may be formed by a plurality of sub-walls rigidly connected to each other.

[0047] The supply pipes 170 a - 170 b are divided into an upstream pipe 170 a between the tank 172 and the cladding 250 and a downstream pipe 170 b inside the cladding 250 to the combustion chamber 158 .

[0048] The enclosure 250 houses the downstream pipe 170b, at least one processing system 202, 204, 206 and the injection zone 210. If dihydrogen leaks from the processing system 202, 204, 206 present in the enclosure 250, the dihydrogen thus remains contained in the enclosure 250 which is closed relative to the rest of the power plant 151.

[0049] Thus, the enclosure 250 forms a containment tank for the dihydrogen around the downstream pipe 170b and the processing systems 202 , 204 , 206 .

[0050] To save material, and thus space and weight, the first wall 251a of the enclosure 250 is formed by a portion of the housing 154. Thus, some of the weight of the enclosure 250 is already included in the weight of the housing 154, and the processing systems 202, 204, 206 are as close as possible to the housing 154 in order to save space around these processing systems.

[0051] The second wall 251b of the enclosure 250 is sealably secured to the housing 154 by any suitable means (eg, welding, rivets with a seal, etc.).

[0052] exist Figure 2 In the illustrated embodiment of the present invention, the upstream pipe 170a is a double-layer pipe including an inner pipe in which dihydrogen flows and an outer pipe surrounding the inner pipe, the outer pipe being evacuated or filled with a gas neutral to dihydrogen (such as dinitrogen).

[0053] Due to the installation of the cladding 250, the downstream pipe 170b is a single-layer pipe extending the inner pipe, while the cladding 250 acts as a double layer, which also simplifies the implementation.

[0054] The tubes 170a-170b sealably pass through the second wall 251b in a feed-through system 258, where only the inner tube passes through the second wall. Such a feed-through system 258 is known to those skilled in the art and will not be described in further detail as it does not directly form part of the present invention.

[0055] To assist the discharge of dihydrogen from the enclosure 250 , the enclosure comprises, in particular on the second wall 251 b , at least one ventilation system 252 a - 252 b which ensures the discharge of the gases present in the enclosure 250 , in particular air and dihydrogen, to the outside of the aircraft 100 .

[0056] exist Figure 2 In the embodiment of the invention shown, the ventilation system 252a-252b takes the form of an air inlet 252a and an air outlet 252b, both of which pass through the second wall 251b. The air inlet ensures the entry of air into the enclosure 250 from outside the aircraft 100, and more particularly here air originating from the secondary flow 20 when the power plant 151 is in operation. The air outlet 252b ensures the discharge of the gases present in the enclosure 250, these gases thus being discharged to the outside of the aircraft 100.

[0057] The gas exhausted through the gas outlet 252 b is directly discharged to the outside of the nacelle 149 by means of a dedicated pipe which emerges to the outside by passing through the fairing 147 or is directly discharged into the secondary flow 20 .

[0058] Alternatively or additionally, the ventilation system 254 takes the form of a pressure limiter 254 which is mounted on the second wall 251 b and through which the gas present in the enclosure 250 is exhausted to the outside of the aircraft 100 .

[0059] Like the gas outlet 252 b , the gas exhausted through the pressure limiter 254 is discharged directly to the outside of the nacelle 149 or directly to the secondary flow 20 by means of a dedicated pipe which emerges to the outside by passing through the fairing 147 .

[0060] The installation of the pressure limiter 254 makes it possible to supplement the gas inlet 252a and the gas outlet 252b, in particular when the pressure in the enclosure 250 increases suddenly and the gas outlet 252b is not sufficient to discharge this excess pressure.

[0061] Figure 3 A power plant 151 according to a second embodiment of the invention is shown, wherein the cladding 350 is formed by a first sub-cladding 350a and a second sub-cladding 350b, the second sub-cladding being separated from the first sub-cladding 350a by a common separation wall 351 .

[0062] The injection zone 210 is arranged in the first sub-cladding 350 a , and the downstream pipe 170 b passes through the second sub-cladding 350 b from the upstream pipe 170 a and in the flow direction of dihydrogen, and then passes through the first sub-cladding 350 a to reach the injection zone 210 by passing through the partition wall 351 .

[0063] Each sub-enclosure 350 a - 350 b is enclosed and defined by a first wall 251 a , a second wall 251 b and a partition wall 351 , and as previously described, the first wall 251 a defining each sub-enclosure 350 a - 350 b is formed by a portion of the outer shell 154 .

[0064] Of course, there may be more than two sub-claddings one after the other.

[0065] According to a particular embodiment, each sub-cladding 350a-350b includes at least one processing system 202, 204, 206. Figure 3 In the illustrated embodiment of the invention, the first sub-enclosure 350a contains the processing systems 204 and 206 (eg, heaters), and the second sub-enclosure 350b contains the processing system 202 (eg, a pump).

[0066] According to a specific embodiment, Figure 3The power device 151 in the embodiment includes a ventilation system 352 in the form of an air inlet 352a passing through the second wall 251b of the first sub-enclosure 350a, an air outlet 352b passing through the second wall 251b of the second sub-enclosure 350b, and an air duct 352c passing through the partition wall 351 and emerging on one side in the first sub-enclosure 350a and on the other side in the second sub-enclosure 350b.

[0067] Thus, an external air flow originating from, for example, the secondary flow 20 enters the first sub-enclosure 350a through the air inlet 352a. The air flow then passes through the first sub-enclosure 350a, where it potentially collects dihydrogen, and thus the gases present in the first sub-enclosure 350a pass through the partition wall 351 via the air passage 352c and enter the second sub-enclosure 350b, where they leave through the air outlet 352b to the outside of the aircraft 100.

[0068] As described above, the gas exhausted through the gas outlet 352 b is directly discharged to the outside of the nacelle 149 or directly discharged into the secondary flow 20 by means of a dedicated pipe that emerges to the outside by passing through the fairing 147 .

[0069] As previously described, the pressure limiter 254 may be mounted on the second wall 251 b of one and / or another of the sub-enclosures 350 a - 350 b .

[0070] Figure 4 A power device 151 according to a third embodiment of the present invention is shown. Figure 3 The same as the second embodiment in, but with a different ventilation system 452.

[0071] This embodiment includes a cladding 350 formed of two sub-claddings 350a-350b and divided by a partition wall 351, wherein the injection zone 210 is arranged in the first sub-cladding 350a, and wherein the downstream pipe 170b passes through the second sub-cladding 350b and then passes through the first sub-cladding 350a to reach the injection zone 210 by passing through the partition wall 351.

[0072] In this embodiment, the second sub-shell 350b is completely surrounded, thereby preventing any dihydrogen that may be present therein from leaving. According to a specific embodiment, the second sub-shell 350b is inerted, for example with dinitrogen, or is evacuated.

[0073] In this embodiment, the downstream pipe 170b sealably passes through the dividing wall 351 in a feed-through system 458. Such a feed-through system 458 is known to those skilled in the art and will not be described in further detail as the feed-through system does not directly form part of the present invention.

[0074] In this particular embodiment, the ventilation system 452 takes the form of an air inlet 452a passing through the second wall 251b of the first sub-enclosure 350a and an air outlet 452b passing through the second wall 251b of the first sub-enclosure 350a. There is therefore no longer an air passage through the partition wall 351.

[0075] Thus, an external air flow originating from, for example, the secondary flow 20 enters the first sub-enclosure 350a through the air inlet 452a. The air flow then passes through the first sub-enclosure 350a, where it potentially collects dihydrogen, and the gas thus present in the first sub-enclosure 350a exits to the outside of the aircraft 100 through the air outlet 452b.

[0076] In this embodiment, the downstream pipe 170b preferably sealably passes through the dividing wall 351 to avoid any passage of dihydrogen originating from leakage within one sub-enclosure 350a-350b to another sub-enclosure 350b-350a.

[0077] As described above, the gas exhausted through the gas outlet 452 b is directly discharged to the outside of the nacelle 149 or directly discharged into the secondary flow 20 by means of a dedicated pipe that emerges to the outside by passing through the fairing 147 .

[0078] As previously described, the pressure limiter 254 may be mounted on the second wall 251 b of one and / or another of the sub-enclosures 350 a - 350 b .

[0079] According to a particular embodiment of the invention, the treatment system 202 is a pump, in particular a high-pressure pump, which is housed in the second sub-enclosure 350b and which propels the dihydrogen to the combustion chamber 158. This installation of the pump alone in the sub-enclosure 350b makes it possible to ensure thermal insulation around the pump.

[0080] Here, the treatment systems 204 and 206 are heat exchangers which ensure heat exchange between the dihydrogen and a heat transfer fluid circulating in exchange tubes 204a-204b and 206a-206b fluidically connected to a heat source.

[0081] In one variation of each of the described embodiments, in order to detect the presence of dihydrogen in the cladding 250 or the sub-claddings 350a-350b, the cladding 250 and each sub-cladding 350a-350b are provided with a monitoring system 264 capable of detecting changes in the cladding 250 and the sub-claddings 350a-350b. The monitoring system 264 may be, for example, a pressure sensor, a dihydrogen detector or other element.

[0082] The power plant 151 includes a shutoff valve 262 installed on the downstream pipe 170b upstream of the first treatment system 202, wherein the shutoff valve 262 can alternately adopt an open position through which dihydrogen can pass or a closed position to prevent dihydrogen from passing. The shutoff valve 262 is preferably an electric, pneumatic or other controlled valve.

[0083] The power plant 151 comprises a control unit 260 connected to each monitoring system 264 and to the shut-off valve 262 and, depending on the information delivered by each monitoring system 264 , the control unit 260 commands the shut-off valve 262 to open when no dihydrogen is detected or to close when dihydrogen is detected.

[0084] To assist in improving the discharge of dihydrogen in the event of a leak in the cladding 250 and each sub-cladding 350a-350b fluidly connected to the gas outlets 252b, 352b, 452b, a fan 266 commanded by the control unit 260 may be installed in the cladding 250 and each sub-cladding 350a-350b.

[0085] Therefore, when the associated monitoring system 264 detects the presence of dihydrogen in the cladding 250 or the sub-claddings 350a-350b, the control unit 260 commands the associated fan 266 to start so as to accelerate the discharge of dihydrogen through the associated outlets 252b, 352b, 452b.

[0086] here Figure 5 The variation is shown as applied to processing system 202 , but may be applied to each of processing systems 204 , 206 .

[0087] In this variation, the processing system 202 is divided into a processing portion 202a and a non-processing portion 202b that are sealed from each other.

[0088] The processing section 202a is a section in which dihydrogen is processed, such as a pipe of an exchanger in which dihydrogen circulates, a section of a pump in which dihydrogen circulates, and the like.

[0089] The non-processing portion 202b is a portion having no dihydrogen therein, such as a pipe in which a heat transfer fluid of an exchanger circulates, a motor of a pump, and the like.

[0090] The second wall 251b is pierced by an opening 502 communicating between the interior of the enclosure 250 or the corresponding sub-enclosures 350a-350b and the exterior of the power device 151 (and here the exterior of the enclosure 250 or the corresponding sub-enclosures 350a-350b).

[0091] The processing system 202 is arranged through the opening 502 and the processing system can be sealably fastened to the second wall 251b so that the processing part 202a is positioned in the enclosure 250 or the corresponding sub-enclosure 350a-350b and the non-processing part 202b is positioned outside the enclosure 250 or the corresponding sub-enclosure 350a-350b.

[0092] According to Figure 6 In one embodiment shown, the control unit 260 includes: a CPU (central processing unit) 601; a RAM (random access memory) 602; a ROM (read-only memory) 603; a storage unit 604 (such as a hard disk) or a storage medium reader (such as an SD (Secure Digital) card reader); and at least one communication interface 605, for example, allowing the control unit to communicate with a monitoring system, a shut-off valve, a fan, etc., connected via a communication bus 600.

[0093] The processor can execute instructions loaded into the RAM from ROM, external memory (not shown), storage media (such as SD card), or communication network. When the device is turned on, the processor can read and execute instructions from the RAM. These instructions form a computer program that enables the processor to implement all or some of the algorithms and steps described.

[0094] All or some of the algorithms and steps described below may be implemented in software by executing a set of instructions by a programmable machine such as a DSP (digital signal processor) or a microcontroller, or in hardware by a machine or dedicated components such as an FPGA (field programmable gate array) or an ASIC (application-specific integrated circuit).

Claims

1. A power device (151) for an aircraft (100), the power device comprising: - Nacelle (149), a propulsion system (150) housed in the nacelle (149) and comprising a core (152) enclosed in a casing (154) and having a combustion chamber (158), - supply pipes (170a-170b) suitable for conveying dihydrogen to the combustion chamber (158) by passing through the housing (154) in the injection zone (210), at least one treatment system (202, 204, 206) arranged on the supply pipe (170a-170b) and suitable for treating the dihydrogen transported in the supply pipe (170a-170b), and a closed enclosure (250, 350) delimited by a first wall (251a) and a second wall (251b) and containing a downstream pipe of the supply pipe (170a-170b), the at least one treatment system (202, 204, 206), and the injection zone (210), wherein the first wall (251a) is formed by a portion of the housing (154), The cladding is formed by a first sub-cladding (350a) and a second sub-cladding (350b), the injection zone (210) is arranged in the first sub-cladding, and the second sub-cladding is separated from the first sub-cladding (350a) by a partition wall (351), wherein the downstream pipe passes through the second sub-cladding (350b) and then passes through the first sub-cladding (350a) by passing through the partition wall (351) to reach the injection zone (210), wherein each of the first sub-cladding and the second sub-cladding is closed and defined by a first wall (251a), a second wall (251b) and the partition wall (351), wherein the first wall (251a) defining each sub-cladding is formed by a portion of the outer shell (154).

2. The power device (151) according to claim 1, wherein: The enclosure (250, 350) comprises at least one ventilation system suitable for discharging the gas present in the enclosure (250, 350) to the outside of the aircraft (100).

3. The power device (151) according to claim 2, wherein: At least one ventilation system takes the form of a first air inlet (252a) and a first air outlet (252b), wherein the first air inlet passes through the second wall (251b) and air from outside the aircraft (100) enters the enclosure (250, 350) through the first air inlet, and the first air outlet passes through the second wall (251b) and gas present in the enclosure (250, 350) is discharged to the outside of the aircraft (100) through the first air outlet.

4. The power device (151) according to any one of claims 2 and 3, wherein: At least one ventilation system takes the form of a pressure limiter (254) which is mounted on the second wall (251b) and through which the gas present in the enclosure (250, 350) is exhausted to the outside of the aircraft (100).

5. The power device (151) according to any one of claims 1 to 4, wherein: The power device comprises a ventilation system (352) in the form of a second air inlet (352a) which passes through a second wall (251b) of the first sub-shell (350a) and through which air from outside the aircraft (100) enters the first sub-shell (350a), a second air outlet (352b) which passes through a second wall (251b) of the second sub-shell (350b) and through which gas present in the second sub-shell (350b) is discharged to the outside of the aircraft (100), and an air duct (352c) which passes through the partition wall (351) and emerges on one side in the first sub-shell (350a) and on the other side in the second sub-shell (350b).

6. The power device (151) according to any one of claims 1 to 4, wherein: The power device comprises a ventilation system (452) in the form of a third air inlet (452a) and a third air outlet (452b), wherein the third air inlet passes through the second wall (251b) of the first sub-shell (350a) and air from outside the aircraft (100) enters the first sub-shell (350a) through the third air inlet, and the third air outlet passes through the second wall (251b) of the first sub-shell (350a) and gas present in the first sub-shell (350a) is discharged to the outside of the aircraft (100) through the third air outlet.

7. The power device (151) according to claim 6, wherein: The downstream pipe can sealably pass through the partition wall (351).

8. The power device (151) according to any one of claims 1 to 7, wherein: At least one of the first sub-enclosure and the second sub-enclosure has a ventilation system in the form of a pressure limiter (254), which is mounted on the second wall (251b) of the at least one sub-enclosure and through which the gas present in the at least one sub-enclosure is discharged to the outside of the aircraft (100).

9. The power device (151) according to any one of claims 1 to 8, wherein: At least one processing system comprises a processing portion (202a) in which dihydrogen is processed and a non-processing portion (202b) in which dihydrogen is not present, wherein the processing portion (202a) and the non-processing portion (202b) are sealed from each other, wherein the processing system is arranged through an opening (502) in the second wall (251b) and is sealably fastened to the second wall (251b), and wherein the processing portion (202a) is positioned in the cladding or a corresponding sub-cladding and the non-processing portion (202b) is positioned outside the cladding or a corresponding sub-cladding.

10. An aircraft (100) comprising a dihydrogen tank (172) and at least one power plant (151) according to one of the preceding claims, wherein: The supply pipes (170a-170b) are fluidly connected to the dihydrogen tank (172).

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